V/stol aircraft with variable tilt wing

ABSTRACT

V/Stol aircraft wiring comprising two independently rotatable fore and aft portions, both portions being movable in any position from the horizontal to the vertical positions for the most aerodynamically efficient configuration for take-off either conventional or vertical, for climb, for landing either conventional or vertical, and for braking either in the air or while taxiing on the ground.

United States Patent Ta Int Ma 30 1972 [s4] V/STOL AIRCRAFT WITHVARIABLE 3,545,701 12/1970 Bertin ..244/| 2 B TILT WING 3.430.894 3/I969 Strand et a].

3,4l0,506 l l/l968 Hayes 1 Inventor: Frederick Tlylm', seamewash-3,136,499 6/1964 Kessler ..244/7 0 73 Th Bod C ,S ttl,W h. I Asslgnee e"8 ompmy ea c as Primary Examiner-Duane A. Reger Filed: 1970At!0rneyGlenn Orlob and Theron H. Nichols [21] App]. No.: 13,422 RACV/Stol aircraft wiring comprising two independently rotatable (gl..244/7C, 244; fore and an portions both portions being movable in yposi [58] Field 7 C 12 A tion from the horizontal to the verticalpositions for the most aerodynamically etficient configuration fortake-oh" either conventional or vertical, for climb, for landing eitherconven- [56] References Cited tional or vertical, and for braking eitherin the air or while tax- UNITED STATES PATENTS 2 011 the ground-3,478,988 I 1/[969 Roed ..244/42 DA 5 China, I5 Drawing FiguresPATENTEUHAY 30 m2 SHEET 10F 8 INVENTOR. FEEDER/CK M. MYLUR BY AGE/v7PAIENTEMY 30 m2 SHEET 2 BF 8 INVENTOR FEEDER/CA M 720101? PATENTEUHMSI912 3 66 6 2 09 sum 3 or e INVENTOR. FEEDER/CK M TAHOE BY 7%; 1 M

PATENIEnm 30 m2 SHEET t BF 8 INVENTOR. FEEDER/CK TAYLOR m PATENTEU m 30W2 SHEET 5 OF 8 INVENTOR. FREDERICK M 7/; no

PATENTEDMAY 3 0 I972 SHEET 6 OF 8 INVENTOR. FREDEIWCK M. 7F4YZOFPATENTEDmao m2 3, 68G 209 sum 8 0F 8 IN VENTOR.

SUMMARY OF THE INVENTION V/STOL aircrafl having a wing comprising two,independently rotatably portions, both portions being rotatable to ahorizontal position parallel to the longitudinal axis of the aircraftfuselage to form a single composite and streamlined wing for cruiseflight and being rotatable to any position between horizontal andvertical positions for various flight and ground maneuvers. Both wingportions or a single portion may be tilted for additional lift, or fortake-off, and only the aft portion may be rotated to the verticalposition on the ground for braking during ground roll.

Accordingly, a primary object of this invention is to provide a superiorwing for an aircraft having two independently rotatable portions forrotating between a horizontal position for level or cruise flight and avertical position for vertical flight.

Another primary object of this invention is to provide a V/STOL aircraftwith a wing that comprises two independently rotatable fore and aftportions wherein in level or cruise flight the leading edge of the aftportion overlaps the trailing edge of the fore portion for forming ahighly efficient single lifting wing and yet can rotate to a verticalposition for vertical tli ht.

another object of this invention is to provide a V/STOL aircraft twoportion wing that has a propulsion system on the fore wing portion forrotating between a horizontal flight position and a vertical flightposition.

A further object of this invention is to provide a V/STOL aircraft twoportion wing in which either one or both wing portions may be rotated ata tilted angle for various flight maneuvers, as climbing or letting downin a landing approach.

Another object of this invention is to provide a V/STOL two portion wingin which the aft wing portion is rotatable to the vertical position forbraking during landing roll.

A still further object of this invention is to provide a V/STOI. twoportion wing in which one or both of the wing portions comprise aplurality of interconnected segments for being adjustable to the desiredaerodynamic configuration.

BRIEF DESCRIPTION OF THE DRAWINGS The drawings diagrammaticallyillustrate by way of example, not by way of limitation, several forms ofthe invention wherein like reference numerals designate correspondingparts in the several views in which:

FIG. 1 is a schematic view in perspective of a VTOL aircraft with thevariable tilt airfoil illustrated in vertical flight configuration;

FIG. 2 is a schematic perspective view of a modification of the VTOLaircraft of FIG. I, illustrated in cruise configuratron;

FIG. 3 is a schematic view in perspective of the VTOL aircraft of FIG. 2in conventional take-off or landing configuration;

FIG. 4 is a schematic view in perspective of the VTOL aircraft of FIG. 2in vertical flight configuration;

FIG. 5 is a schematic perspective view of the VTOL aircraft of FIG. 2 inan inflight or a landing roll braking configuration;

FIG. 6 is a detailed cross sectional view of the two, independentlyrotatable wing portions taken at 66 on FIG. 2;

FIG. 7 is a view of the variable tilt airfoil of FIG. 6 illustratingfour basic positions beyond cruise position which the airfoil aftportion may assume;

FIG. 8 is the two, independently rotatable wing portions of FIG. 6rotated to the vertical flight configuration;

FIG. 9 is a top view of FIG. 6;

FIG. 10 is a schematic sectional view similar to FIG. 6, but of amodified segmented wing in cruise position;

FIG. 11 is a sectional view of the modification of FIG. 10, rotated tothe vertical flight configuration;

FIGS. 12 to 15 are schematic sectional views of the modification of FIG.10 showing only a few of the various configurations possible with thesegmented fore and aft wing portions.

DESCRIPTION OF THE PREFERRED EMBODIMENTS The invention, the scope ofwhich being defined in the appended claims, is not limited in thisapplication to the details of construction and arrangement of partsshown and described, since the invention is capable of other embodimentsand of being practiced or carried out in various other ways. Also, it isto be understood that the phraseology or terminology employed herein isfor the purpose of description and not of limitation.

The variable tilt airfoil described hereinafter provides a wing whichfacilitates vertical take-offs and landings, lift augmentation forconventional take-offs and landings and improved ground roll braking byrotating a portion of the wing to the vertical position.

FIG. I illustrates a typical V/STOL aircraft 1 0. This aircraft 10comprises a conventional fuselage 11 with a conventional tail Q andallochiral wings I 3 and 1 3 a. Wing L3, for example, comprises two,fore and aft portions L4 and 1 5 and right wing lia comprises fore andaft portions Ila and l 5a. The aircraft propulsion means l 6 comprises ajet engine l 7 mounted in the fuselage Q and prop gear train l 8 fixedlymounted on the forward wing portion 1 4. Right wing I 3a likewise hasits propulsion means l 6 a comprising jet engine Ila and prop gear trainlja. Any suitable pilot controlled actuating mechanism is included inthe fuselage l l for rotating wing portions g and L5 to the variouspositions in the of motion illustrated hereinafter. An airfoil Q withailerons l l is fixed to the ends of wing spars (not shown in FIG. 1).

FIG. 2 illustrates a modification of the V/STOL aircraft of FIG. 1,wherein the wings are shown rotated to the cruise or horizontal flightposition. In this modification the lateral control system or ailerons 20 are mounted on fixed airfoils l outboard of the wing fore and aftportions 1 4 and Q. Likewise, a fixed airfoil section A is positionedbetween the rotatable wing portions and the fuselage.

FIG. 3 is a schematic perspective view of the aircraft of FIG. 2 shownin climbing configuration wherein only the wing aft portion isillustrated as rotated slightly for increased lift.

FIG. 4 is a perspective view of the aircraft of FIG. 2 shown with bothfore and aft wing portions 5 and Q of the aircraft rotated to thevertical position.

FIG. 5 is a view of the modification of FIG. 4 wherein the wing afiportion is positioned vertically for braking during a landing roll orfor aerodynamic braking for fast let downs.

FIG. 6, a detailed sectional view taken at 2-2 on FIG. 2 illustrates thenovel cooperation between the fore and aft wing portions Q and Q mountedon fore and aft wing spars 2 2 and Q, respectively. Fore wing portion1;! rotatably mounted on fore spar 2 2 has leading edge part A andtrailing edge part L5 having flap ZQrotatably mounted thereon. Wing aftportion E has leading edge part3! and trailing part 2 As illustrated inthe cruise position, leading edge part 2 7 of the wing aft portion LSoverlies the trailing edge part 25 and flap 2 6 of the wing fore portionH to form a very efficient and streamlined single lifting high speedwing.

As described above, suitable actuators (not shown) are mounted in theaircrafi for rotating each of wing portions IQ: and gs about fore andaft wing spars 21 and 23, respectively.

FIG. 7, a sectional view of the wing of FIG. 6, shows the aft wingportion 15b rotatable in four different positions, for example, beyondthe horizontal, the vertical position being shown in sectional lines andthe other intermediate position being shown in broken lines. Likewise,in all positions of the aft wing portion beyond the horizontal position,a slot 22 is formed between the two wing portions. This slot 2 9 isclosed or opened by controllable flap 2 6 described above in relation toFIG. 6.

FIG. 8 is another detail view of the FIG. 6 embodiment where both thefore and aft wing portions are rotated to the vertical position. Thebroken line outline of the wing shows the horizontal position of the twowings when fitted together for horizontal flight.

H6. 9, a top view of the embodiment of FIG. 6, illustrates the engine orpower means ll: which is connected to the fore wing portion in andextends rearwardly whereby a cutout 3 0 is formed in the leading edge ofthe aft wing portion.

FIG. 10, is another modification wherein the fore and aft wing portionsare divided into segments, fore wing portion 11c comprising forward wingpart 2 4 with a propulsion engine (not shown) mounted thereon and aftwing part Q1 which is rotatable about fore wing spar 2 2. Pivotallyconnected to the aft wing pang is a flap a. Aft wing portion l ccomprises forward leading edge flap Q pivotally connected to pivotalsegment Q which in turn is pivotally mounted on wing rear spar Q. An aftpivotal part 3 4 is pivotally mounted for rotation about wing rear spar2 3 and pivotally connected to the rearward end of segment 3 4 istrailing edge flap as. Each segment of each of the two wing portions l 4c and g are individually controllable and operable by conventionalactuators controlled by the pilot.

FIG. 11 shows both segmented wing portions lie and liq rotated to thevertical position for vertical flight, propulsion engine 1Q) beingfixedly mounted on leading edge segment 25 of wing fore section 13.

FIGS. 12-15 are schematic sectional views of the modification of FIG.wherein various configurations that are possible are shown with thesegmented fore and aft wing portions.

In FIG. 12, fore segmented wing section 1 c is shown wherein thesegments 2 4, 3 1, and l are aligned for best aerodynamic flow for avery steep climb, leading edge segment 2 4 carrying the propulsionengine E. Aft wing section E, including segments 3 2, Q, 3 4 and 3 5,are aligned also for best aerodynamic flow for a steep climb as combinedwith the fore wing section.

FIG. 13 shows the segmented wing portions 11c and g: in alignmentforming one continuous streamline horizontal wing.

FIG. 14 shows the segmented wing portions a: and lie wherein all arecurved in an arcuate manner for best aerodynamic air flow, or anotherhigh lift configuration.

FIG. 15 shows the segmented wing portions 1i: and .gc with fore portion5c in horizontal position and segmented aft portion 1iin verticalposition for greatest or maximum aerodynamic flow for aerodynamicbraking either in flight or on the ground.

In summary, a new V/STOL aircraft has been disclosed having twoindependently rotatable portions forming the wing which rotate between ahorizontal position for level or cruise flight and a vertical positionfor vertical flight. Likewise, this aircraft with the two fore and aftwing portions also forms a highly efficient single lifting wing whenrotated to the horizontal position. In this two portion wing also, theaft portion may be rotated to the vertical position for braking duringeither a landing roll or aerodynamic braking while flying in the air.Likewise is shown an aircraft having a wing in which the complete wingis divided into independently movable portions or a wing in which one ormore portions of it are fixed airfoils interconnecting the wing spars.Also, the wing of an aircraft is disclosed in which the two portions aredivided into segments. One embodiment FIG. 1 has a wider fixed airfoilat the tip and another embodiment FIGS. 2 and 3 have, additionally, afixed airfoil inboard of the two wing portions.

Thus it may be seen that the disclosed two independently rotatable foreand aft wing portions provide a variable lift wing for a V/STOL aircraftin a manner which meets each of the objects set forth above.

What is claimed is:

I. An aircraft having VISTOL capability with a fuselage and wing, saidwing comprising: an inboard spanwise wing section having its aerodynamiccomposite airfoil section divided chordwise into a fore and an afttilt-wing portion; said fore tiltwing portion being pivotally mounted tothe fuselage for rotation with respect to the fuselage about a firstspanwise axis; said fore tilt-wing portion having a leading edge partmounted on a wing spar axially aligned with said first spanwise axis,said leadin edge part having a trailing ed e part with a flap rotata lymounted thereon for varying the airfoil camber of said fore tilt-wingportion; said afi tilt-wing ponion being pivotally mounted to thefuselage for rotation with respect to the fuselage about a secondspanwise axis which is in parallel alignment with said first spanwiseaxis and displaced chordwise aft of said first spanwise axis; said afttilt-wing portion being mounted on a wing spar axially aligned with saidsecond spanwise axis for independent rotation with respect to both saidfore tilt-wing portion and said fuselage; propeller propulsion meansfixedly mounted on said fore tilt-wing portion of the inboard spanwisewing section and tiltable in unison therewith about said first spanwiseaxis for moving the aircraft forwardly when said fore tilt-wing portionis in the horizontal position and moving the aircraft vertically whensaid fore tiltwing portion is rotated to the vertical position; each ofsaid fore and aft tilt-wing portions being independently movable tovarious positions from a horizontal position substantially parallel tothe fuselage longitudinal axis for forward cruise flight, to a verticalposition substantially perpendicular to said fuselage longitudinal axisfor vertical flight; an outboard spanwise fixed wing portion fixedlymounted to the wing spars of the fore and aft tilt-wing portions andpositioned outside of the slipstream of said propeller propulsion meansmounted to the inboard spanwise tilt-wing sections, for producing anaerodynamic lifting force during transition flight of the aircraft froma vertical flight condition to forward cruise flight; and lateralcontrol system ailerons pivotally mounted on said fixed wing portionsfor producing lateral control during transition and forward flight.

2. An aircraft as recited in claim I, wherein, said fore portion havingthe propeller propulsion means mounted thereon is positioned at saidhorizontal position and said aft portion is rotated relative to saidfore portion to said vertical position for deflecting the propellerslipstream normal to the longitudinal axis of the fuselage and provideaerodynamic braking.

3. An aircraft as recited in claim 1, wherein, said fore and aftportions have a leading and trailing edge; and when said fore and aftportions are rotated to said horizontal position they are in abutmentrelation forming a substantially continuous upper and lower surface withthe leading edge of said aft portion overlapping the trailing edge ofsaid fore portion for forming a single composite airfoil section.

4. An aircraft as recited in claim 1, further including: a trailing edgemovably mounted on said fore portion; and when said aft portion isrotated relative to said fore portion so as to form a slot therebetween,the trailing edge is positionable to open and close said slot forcontrol of the air flow through chordwise composite wing of theaircraft.

5. An aircraft as recited in claim 1, wherein, said fore and aftportions comprise a series of chordwise segments movably interconnectedand positionable to vary the curvature of the upper surface of said foreand aft portions to the desired aerodynamic configuration for V/STOLcapability.

l l k

1. An aircraft having V/STOL capability with a fuselage and wing, saidwing comprising: an inboard spanwise wing section having its aerodynamiccomposite airfoil section divided chordwise into a fore and an afttilt-wing portion; said fore tilt-wing portion being pivotally mountedto the fuselage for rotation with respect to the fuselage about a firstspanwise axis; said fore tilt-wing portion having a leading edge partmounted on a wing spar axially aligned with said first spanwise axis,said leading edge part having a trailing edge part with a flap rotatablymounted thereon for varying the airfoil camber of said fore tilt-wingportion; said aft tilt-wing portion being pivotally mounted to thefuselage for rotation with respect to the fuselage about a secondspanwise axis which is in parallel alignment with said first spanwiseaxis and displaced chordwise aft of said first spanwise axis; said afttilt-wing portion being mounted on a wing spar axially aligned with saidsecond spanwise axis for independent rotation with respect to both saidfore tilt-wing portion and said fuselage; propeller propulsion meansfixedly mounted on said fore tilt-wing portion of the inboard spanwisewing section and tiltable in unison therewith about said first spanwiseaxis for moving the aircraft forwardly when said fore tilt-wing portionis in the horizontal position and moving the aircraft vertically whensaid fore tilt-wing portion is rotated to the vertical position; each ofsaid fore and aft tiltwing portions being independently movable tovarious positions from a horizontal position substantially parallel tothe fuselage longitudinal axis for forward cruise flight, to a verticalposition substantially perpendicular to said fuselage longitudinal axisfor vertical flight; an outboard spanwise fixed wing portion fixedlymounted to the wing spars of the fore and aft tilt-wing portions andpositioned outside of the slipstream of said propeller propulsion meansmounted to the inboard spanwise tilt-wing sections, for producing anaerodynamic lifting force during transition flight of the aircraft froma vertical flight condition to forward cruise flight; and lateralcontrol system ailerons pivotally mounted on said fixed wing portionsfor producing lateral control during transition and forward flight. 2.An aircraft as recited in claim 1, wherein, said fore portion having thepropeller propulsion means mounted thereon is positioned at saidhorizontal position and said aft portion is rotated relative to saidfore portion to said vertical position for deflecting the propellerslipstream normal to the longitudinal axis of the fuselage and provideaerodynamic braking.
 3. An aircraft as recited in claim 1, wherein, saidfore and aft portions have a leading and trailing edge; and when saidfore and aft portions are rotated to said horizontal position they arein abutment relation forming a substantially continuous upper and lowersurface with the leading edge of said aft portion overlapping thetrailing edge of said fore portion for forming a single compositeairfoil section.
 4. An aircraft as recited in claim 1, furtherincluding: a trailing edge movably mounted on said fore portion; andwhen said aft portion is rotated relative to said fore portion so as toform a slot therebetween, the trailing edge is positionable to open andclose said slot for control of the air flow through chordwise compositewing of the aircraft.
 5. An aircraft as recited in claim 1, wherein,said fore and aft portions comprise a series of chordwise segmentsmovably interconnected and positionable to vary the curvature of theupper surface of said fore and aft portions to the desired aerodynamicconfiguration for V/STOL capability.